Numercial simulation of transonic axial compressor rotor flow with tip clearance using multi-block meshes
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摘要: 开发了三维数值模拟程序研究轴流跨音转子叶尖间隙流动,应用高雷诺数k-ε湍流模型加壁面函数的方法,计算了轴流跨音转子NASA Rotor37在设计转速下的流场.叶尖间隙采用分区的H型网格和主流区连续对接耦合计算,没有用间隙模型,也没有考虑Vena收缩效应而减小间隙量.在用有限体积法对Navier-Stokes方程和湍流方程进行空间离散的过程中采用了交错网格的方法将N-S方程与湍流方程紧密地耦合在一起,从而提高了计算精度.计算结果和实验数据进行了详细的比较和分析.结果表明,中部叶展具有与实验结果非常一致的流场特征,根、尖区流场则因涡粘假设和激波问题的存在而使流动细节与实验结果略有偏差.Abstract: To investigate the tip clearance flow in transonic compressor rotor, a 3D numerical simulation code was developed. The 3D flow fields of a transonic axial compressor, NASA Rotor 37, with considering the tip clearance were simulated using Reynolds-averaged Navier-Stokes equations with high Reynolds-Number k-ε turbulence model and wall function. A multi-block grid was used for the tip clearance domain of the rotor, which couples with the main flow without any tip clearance experiential models, as well as avoids reducing the tip clearance scale under the assumption of Vena convergence effects. The Navier-Stokes equations and turbulence equations were strongly coupled by staggered finite volume scheme in order to get more precise results. The 3D simulation results were compared with the experimental data. The mid-span flow structures are consistent with experimental result, as well as the slight different details exist in the tip and hub flow structures because of the eddy viscosity model and shock-wave.
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Key words:
- grids /
- numerical computation /
- \%k-ε\% turbulence model /
- staggered mesh scheme
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